Amphibian aeroplane



FIPB206 June 4, 1935. R. RAND, JR

AMPHIBIAN AEROPLANE Filed Jan. 14, 1932 10 Sheets-Sheet 1 INVENTOR R. mM m A Z 5 June 4, 1935. R, R. RAND, JR

AMPHIBIAN AEROPLANE Filed Jan. 14, 1932 10 Sheets-Sheet 2 N VE N TORFun/s ii. far/v17 JR- y A TTORNEYS June 4, 1935. R. R. RAND, JR

AMPHIBIAN AEROPLANE Filed Jan. 14, 1932 INVENTOR. Furl/5 ii. fim/D Jrv.

June 4, 1935. R. R. RAND, JR

AMPHIBIAN AEROPLANE Filed Jan. 14, 1932 10 Sheets-Sheet 4 INVEN TOR.Furl/s I? 75MB BY I WM ATTORNEYS.

June 4, 1935. R. R. RAND, JR

AMPHIBIAN AEROPLANE Filed Jan. 14, 1932 10 Sheets-Sheet 5 VENTOR 44/5 I?lfk f T ZKMM ATTORNEY June 4, 1935. R R RAND, JR 2,003,975

AMPHIBIAN AEROPLANE Filed Jan. 14. 1932 10 Sheets-Sheet 6 ATTORNEY June4, 1935.

R. R. RAND, JR

ATTORNEY f ZM June 4, 1935. R. R. RAND. JR

AMPHIBIAN AEROPLANE Filed Jan. 14, 1932 10 Sheets-Sheet 9 June 4, 1935.

R. R. RAND, JR

AMPHIBIAN AEROPLANE Filed Jan. 14, 1932 10 Sheets-Sheet l0 BY fgATTORNEY Patented June 4, 1935 UNITED STATES PATENT OFFICE 11 Claims.

This invention relates to an aeroplane. While many of the features ofthe invention can be used in either a land plane or a hydroplane, in theembodiment of the invention illustrated the aeroplane of this inventionas shown is of the amphibian type the same thus being capable of landingon and taking off from either land or water.

It is desirable in an aeroplane to have a supporting structure for thehull and wings, as well as for the motor and other necessary parts,which is of maximum strength and of minimum weight.

It is also desirable to have the concentrated loads compactly arrangedand so that the center of gravity of the plane is quite low. This givesgreat stability, preventing lateral tipping when the plane is on theWater, eliminating the tendency to nose over when the plane is alightingon the land and making the plane easy to maneuver.

It is also desirable in a plane to have the parts forward of the pilotand passengers unobstructed, and to have the propeller in the rear ofthe pilot and passengers.

It is also desirable to have the propeller at a sufficient height, sothat there will be no slip stream over the fuselage and the resistanceof the air to the plane will be lessened and a high efficiency ofpropeller action obtained.

It is also desirable from the standpoint of appearance and performanceto have the plane arranged with smooth lines or surfaces and a minimumof projecting parts.

It is an object of this invention, therefore, to provide an aeroplanehaving a hull or fuselage, a propeller, a propeller support and a motor,said propeller being disposed entirely above the remainder of the planesave the propeller support, together with means for driving saidpropeller from said motor.

It is a further object of the invention to pro vide an aeroplane havinga hull or fuselage, a wing extending transversely above said hull, apropeller disposed entirely above said wing and rotatable about ahorizontal axis, a motor disposed below the top of the wing, togetherwith means for driving said propeller from said motor.

It is an object of this invention, also, to provide an aeroplane of theamphibian type having the hull designed to move efiiciently in or on thewater, and having landing gear comprising wheels, which wheels areretractible into the hull when the plane is to alight on or move on thewater.

It is still another object of the invention to provide an aeroplanehaving a hull, a motor disposed quite low within said hull to give a lowcenter of gravity, a propeller disposed above the hull and wing, andtransmission mechanism for driving said propeller from said motor.

It is a further object of the invention to provide an aeroplane having acentral frame, a motor suspended from said frame, a hull suspended fromsaid frame, and wings having frames secured at either side respectivelyto said frame.

It is also an object of the invention to provide an aeroplane as setforth in the preceding paragraph, together with an auxiliary framesecured rigidly to said motor and extending from said frame, a propellercarried by said auxiliary frame, and means for driving said propellerfrom said motor.

It is still another object of the invention to provide an aeroplanecomprising a frame, a hull carried by said frame, a motor suspended fromsaid frame and disposed within said hull, an auxiliary frame secured toand extending up wardly from said motor, a propeller shaft carried atthe upper end of said auxiliary frame, andmeans extending from saidmotor to said shaft for driving the same.

It is a further object of the invention to provide an aeroplane as setforth in the preceding paragraph, the same having a casing surroundingthe upper part of said auxiliary frame, which may be narrow and ofstream-line shape, and extending from the top of the hull to and abovethe propeller shaft, a propeller being disposed in the rear of thiscasing.

It is also an object of the invention to provide an aeroplane having ahull of general stream-line shape with continuous lines or surfaces atthe sides thereof, said hull having compartments within its sidesadapted to receive the landing wheels when retracted, said hull having amain compartment which is water-tight and independent of said firstmentioned compartments.

It is also an object of the invention to provide an aeroplane having aframe, a hull, together with novel and efficient means for suspendingthe hull from said frame.

It is still another object of the invention to provide an aeroplanehaving a light and simple frame, means for suspending the power plantincluding the propeller drive and support from said frame includingresilient means between said frame and power plant, whereby vibration islessened.

It is more specifically an object of the invention to provide anaeroplane having a hull construction of great strength and yet which isquite light in weight, said hull being supported by a truss frame ofnovel and efficient design, said plane having a landing gear of novelform with novel means for retracting the same into a compartment in thehull, together with novel means for opening and closing saidcompartment.

These and other objects and advantages of the invention will be fullyset forth in the following description made in connection with theaccompanying drawings, in which like reference characters refer tosimilar parts throughout the several views and in which:-

Fig. 1 is a top plan view of the aeroplane;

Fig. 2 is a view in side elevation of said aeroplane;

Fig. 3 is a view in front elevation of said aeroplane;

Fig. 4 is a partial plan view shown on an enlarged scale;

Fig. 5 is a partial view in side elevation shown on an enlarged scale;

Fig. 6 is a partial view in rear elevation with some parts broken away,also shown on an enlarged scale;

Fig. 7 is a vertical section on line 1--1 of Fig. 4, as indicated by thearrow;

Fig. 8 is a vertical section taken on line 8-8 of Fig. 4, as indicatedby the arrow;

Fig. 8a is a vertical section taken on line 8w-8a of Fig. 4;

Fig. 9 is a top plan view of the frame used, also showing the motor andmotor support;

Fig. 10 is a front view of the frame structure, a part thereof beingbroken away;

Fig. 11 is a vertical section showing the main frame taken on line ofFig. 10, as indicated by the arrow;

Fig. 12 is a view in side elevation of the auxiliary frame;

Fig. 13 is a view in front elevation of the auxiliary frame;

Fig. 14 is a view in rear elevation of the auxiliary frame;

Fig. 15 is a top plan view of the supporting hearing structure for themotor;

Fig. 16 is a section on line |6-|6 of Fig. 15, as indicated by thearrow, Figs. 15 and 16 being shown on an enlarged scale;

Fig. 17 is a partial section taken on line |1|1 of Fig. 18 which issubstantially the same as line 1--1 of Fig. 4;

Fig. 18 is a top plan view of the parts shown in Fig. 17;

Fig. 19 is a view as seen from the right of Fig. 17;

Fig. 20 is a partial transverse section of the hull taken substantiallyon line 20-20 of Fig. 2;

Fig. 21 is a horizontal section taken on line 2 |-2| of Fig. 20, asindicated by the arrows;

Fig. 22 is a horizontal section taken on line 22-42 of Fig. 20, asindicated by the arrows;

Fig. 23 is a vertical section taken on line 23-23 of Fig. 20, asindicated by the arrows;

Fig. 24 is a view in side elevation of the keel structure;

Fig. 25 is a vertical section taken on line 25-45 of Fig. 24, asindicated by the arrows;

Fig. 26 is a vertical section taken on line 26-26 of Fig. 24, asindicated by the arrows;

Fig. 27 is a top plan view of Fig. 24;

Fig. 28 is a view in side elevation of the wheel retracting mechanism;

Fig. 29 is a view as seen from the right of Fig. 28;

Fig. 30 is a partial view of the parts shown in Fig. 29 shown on anenlarged scale;

Fig. 31 is a vertical section on line 3|-3| of Fig. 30, as indicated bythe arrow.

Fig. 32 is a view partly in side elevation and partly in verticalsection of some of the parts shown in Fig. 28 on an enlarged scale;

Fig. 33 is a perspective view of the main frame used;

Fig. 34 is a. view partly in side elevation and partly in verticalsection, illustrating the defiector in the wheel pocket;

Fig. 35 is a view similar to Fig. 18, showing a resilient support forthe hull;

Fig. 36 is a view in elevation as seen from the right of Fig. 35; and

Fig. 37 is a view in front elevation of the. parts shown in Fig. 35.

Referring to the drawings, particularly Figs. 1 to 3, an aeroplane isshown comprising a hull referred to generally as 40 and having wings 4|extending at either side thereof, and it will be noted, as clearly shownin Fig. 3, that the top wing surface over the hull is continuous withthe top surface of the wings at the sides of the hull and insubstantially the same plane. The wings 4| are shown as having theailerons Ma. The plane also has the vertical tail rudder 42 and thehorizontal stabilizer 43. A tower 44 of narrow stream-line shape risesfrom the top and central part of the hull or top of the wing and carriesat its upper rear side the propeller 45. A rear landing wheel 46 isshown at the central bottom portion of the hull, the same being carriedon a bracket 41, said wheel being partially recessed in said hull. Thehull forward of the tower 44 has a cockpit 48 having a windshield 49 atthe front thereof, the same being entered by a door 40a in the side ofthe hull which is hinged at one vertical side thereof.

The hull 40 is secured to and supported by a main frame illustrated inFigs. 4, 5, 9, 10, 11 and 33. This frame is disposed in the central partof the wing over the hull. It is formed of trusses or beams andcomprises four main members 50, 5|, 52 and 53 which are parallel andspaced to form a quadrilateral. Members 50 and 5| are in the samevertical plane and located at the forward end of the frame, whilemembers 52 and 53 are also in the same vertical plane and disposed atthe rear of the frame, and are somewhat closer together than members 5|and 52. Member 53 is also at a slightly lower point than member 5|. Saidmain frame will be designated as a whole as 55. While members 50 to 53might be of different forms, in the embodiment of the inventionillustrated they are shown as made of tubes. Members 50 and 52 areconnected by parallel members 56, 51, 58 and 59. The members 56, 51, 59and 58 are spaced substantially equally, the space between members 51and 59 being slightly greater than the space between the others. Members56 to 59 are also illustrated as tubular in form and they are weldedsecurely to members 50 and 52. Members 5| and 53 are connected by fourparallel members 60, BI, 62 and 63. It will be seen that members 6| and62 are spaced much farther apart than are members 51 and 59. Members 60to 63 are also illustrated as tubes and these are welded securely tomembers 5| and 53. It may be stated that gusset plates such as shown atthe junction of members 51 and 52 and designated 64, are used at thejunctions of tubes connecting members 50 and 52 and members 5| and 53and at other places where the tubes are welded together, these gussetplates not being shown in most instances. The members 58 and 59 areconnected substantially midway between members 50 and 52 by member 65extending parallel to members 50 and 52 and members 58 and 59 arefurther connected by the diagonal members 66 and 61 extending fromopposite ends respectively of members 65 to the opposite corners of therectangle formed by members 50, 52,

58 and 59. The members 66 and 61 are thus parallel. Members 65, 66 and61 are also shown in the form of tubes and these are welded securely tothe tubes at their ends. Members 56 and 51 are likewise connected by themember 68 extending parallel to and midway between members 50 and 52 anddiagonal members 69 and 18 analogous to members 66 and 61 also extendfrom the opposite ends of member 68 to opposite corners of the rectangleformed by members 50, 52, 56 and 51. It will be noted that members 69and 10 extend in opposite directions to members 66 and 61. The gussetplates 64 are connected by strong wire members 1| extending diagonallyof the rectangle formed by members 59, 52, 51 and 59. Members 62 and 63at the bottom of the frame are connected by tubes 12 extending parallelto members 5| and 53, said tubes being welded to the tubes 62 and 63. Adiagonal tube 13 extends from the junction of the forward tube 12 andtube 63 forwardly and inwardly to the junction of the rear tube 12 andtube 62. Other diagonal tubes 14 are provided, the forward one of whichextends from the junction of the forward tube 12 and tube 63 forwardlyand inwardly to the junction of tubes 62 and 5|. The rear diagonal tube14 extends from the junction of the rear tube 12 and tube 62 rearwardlyand outwardly to the junction of the tubes 63 and 53. Tubes 15corresponding to tubes 12 extend between tubes 68 and 6|, being weldedsecurely thereto at their ends. The diagonal tube 16 corresponding totube 13 extending oppositely thereto extends between the inner end ofthe forward tube 15 to the outer end of the rear tube 15, the same beingsecurely welded at its end to tubes 69 and 6|. Diagonal tubes 11corresponding to tubes 14 are provided, the rear one of which extendsfrom the lower outward corner of the frame formed by tubes 69 and 53inwardly and forwardly to the junction of tubes 15 and 6|. The frontdiagonal tube 11 extends from the junction of tube 6| and tube 5|rearwardly and outwardly to the junction of tube 15 and tube 68. It willbe seen from the description already made and that to follow, that frame55 is symmetrical about a line drawn midway between and parallel totubes 56 and 58. A tube 18 extends from the junction of tubes 51 and 52downwardly and outwardly to the junction of tubes 62, 12, and 14. Acorresponding tube 19 extends from the junction of tubes 59 and 52downwardly and outwardly to the junction of tubes 6|, 15 and 11. Anothertube 89 extends from the junction of tubes 51 and 68 downwardly,outwardly and rearwardly to the junction of tubes 62, 12 and 14, and acorresponding tube 8| extends downwardly, outwardly and rearwardly fromthe junction of tubes 59 and 65 to the junction of tubes 6|, 15 and 11.Tubes and 8| are welded securely to the tubes 6| and 62 respectively attheir lower ends and to the tubes 51 and 59 respectively at their upperends. Another tube 82 extends from the under side of tube 51substantially at the junction of tube 68 therewith, downwardly,outwardly and forwardly to tube 62 at the junction of tube 12 therewith.The corresponding member 83 extends from the under side of tube 59substantially at the junction therewith of tube 65 downwardly, outwardlyand forwardly to tube 6| substantially at the junction of tube 15therewith. Another tube 84 extends from the junction of tubes 50 and 51downwardly, outwardly and rearwardly to tube 62 substantially at thejunction of tube 12 therewith. The corresponding tube 85 extends fromthe junction of tubes 59 and 50 downwardly, outwardly and rearwardly totube 6| substantially at the junction of tube 15 therewith.

Four split or cap bearings 86 are provided, disposed within and somewhatbelow the tubes 62 and 6| and the tube 81 extends from the under side oftubes 51 and 52 substantially at the junction thereof downwardly,inwardly and forwardly to a bearing 86. A corresponding tube 88 on theother side of the frame extends from the under side of the tubes 59 and52 substantially at the junction thereof downwardly, inwardly andforwardly to a bearing 86. Another tube 89 extends from the under sideof tube 51 substantially at the junction of tube 68 therewithdownwardly, inwardly and rearwardly to bearing 86. The correspondingtube 90 at the other side of the frame extends from the under side oftube 59 substantially at the junction of tube 65 therewith inwardly andrearwardly to a bearing 86. A tube 9| extends from tube 62 substantiallyat the junction of tubes 12, 14, 18 and 80 therewith inwardly andslightly forwardly and downwardly to bearing 86. A tube extends from theunder side of tube 51 substantially at the junction of tube 68 therewithdownwardly, inwardly and forwardly to bearing 86 and a correspondingtube 96 at the other side of the frame extends from the under side ofthe tube 59 substantially at the junction of tube 65 therewithdownwardly, inwardly and forwardly to a bearing 86. A tube 91 extendsfrom tube 62 substantially at the junction of tubes 12, 13, 82 and 84therewith inwardly and slightly downwardly and forwardly to a bearing 86and a corresponding tube 98 on the other side of the frame extends fromtube 6| substantially at the junction of tubes 15, 16, 83 and 85therewith inwardly and slightly forwardly and downwardly to a bearing86. A tube 99 extends from the junction of tubes 51 and 59 downwardly,inwardly and rearwardly to a hearing 86 and a corresponding tube I00extends from the junction of tubes 59 and 50 rearwardly, downwardly andinwardly to a bearing 86. It will be noted that each bearing 86 hasthree supporting tubes extending thereto. These three tubes form atripod which support said bearing from the frame 55. The tubes extendingto the a plate 860 of semi-cylindrical form having a flange 86doverlying the flange 86b and also having a central vertical plate 86c.Plate 86a also has a vertical plate 86f which extends along the outerside of and is welded to the tube 9| or the lower tube extending to thebearing. Gusset plates 93 are also shown between the tubes converging atbearing 86. The cap 860 of the bearing is secured thereto by headed andnutted bolts 94.

It will be seen that when caps 860 are removed, members I09 and H9 canbe lifted vertically and will clear the frame pieces 81, 89 and 9|.

The main frame proper also includes a tube ||l| extending from the underside and one end of tube 50 downwardly and inwardly to tube 5|substantially at the junction of tube 62 therewith, and a tube |0|aextends from the under side of tube 50 substantially at the junction oftube 51 therewith downwardly and outwardly to tube 5| substantially atthe junction of tube 62 therewith. Tubes I M and I Ia are thus invertical alinement with tubes 50 and I. Corresponding tubes I02 and I03extend downwardly from the under side of tube 50 substantially at thejunction therewith of tubes 59 and 58 to tube 5I substantially at thejunction therewith of tube 8|. Tubes I04 and I05 at the rear end of theframe extend from the under side of tube 52 substantially at thejunctions therewith of tubes 55 and 51 respectively downwardly to tube53 substantially at the junction therewith of tube 52. Correspondingtubes I06 and I0! extend from the under side of tube 52 substantially atthe junctions therewith of tubes 58 and 59 downwardly to tube 53substantially at the junction therewith of tube 6|. The main frame 55also includes vertical members I08 at the four corners thereof whichextend between members 52 and 53 at the rear and between members 50 and5| at the front. These members, like the other members of the truss areformed of tubes and are welded securely at their ends to members 50, 5|,52 and 53. The side of the main frame formed between members 58, 80 andI08 has truss members I08a therein, two of which extend from the cornersof said side at the junction of tubes I08 and 50 downwardly to tube 60substantially at the junction therewith of tubes I5. The other or innermembers I08a extend from member 58 substantially at the junctiontherewith of tube 65 downwardly in diverging relation to tube 60adjacent the ends of the other tubes I08a. The side of the main frameformed by members I08, 56 and 53 also have truss members I081) therein,the outer ones of which extend from the corners of the frame and tube 56downwardly in converging relation to tube 63 substantially at thejunction therewith of tubes 12. The other or inner members I091) extendfrom tube 56 substantially at the junction therewith of tube 68downwardly in diverging relation to tube 63 adjacent the ends of theother tubes I08b. It will thus be seen that the main frame 55 is a rigidopenwork frame having trusses at its four vertical sides and havingtrusses at its top and bottom at either side, disposed in the plane ofits top and bottom members. There are also inclined truss framesinwardly of the side trusses, which inclined trusses extend betweenmembers 51 and 62 on one side and 59 and BI on the other side. The trussat the front of the frame including members 50 and 5I is made rigid bystrong wires I 02a which extend respectively between tubes 50 and 5I anddiagonally between the ends of members IOIa and I03. The vertical trussat the rear of the frame is likewise made rigid by strong wires I04awhich extend between tubes 52 and 53 and diagonally between the ends oftubes I05 and I 01. The bearings 86 receive tubular members I09 to whichreference will later be made.

As shown in Figs. 5 and 10, the main frame 55 is above the hull properand forms the framework for the central portion of the wing. The centralportion of the wing might be called the trunk portion of the aeroplane.The main frame within this trunk portion carries all of the load and allof the load stresses, and practically all other stresses are transmittedto this frame. The side sections of the wing or wings 4| also have trussframes therein which extend from each side of and are rigidly connectedto frame 55.

The frame 55 has lugs II3 projecting laterally at the ends of members50, 5|, 52 and 53 and these lugs are embraced by the bifurcated ends oftubular truss members H4 and H5 as indicated in Figs. 9 and 10. Saidmembers H4 and H5 form the top and bottom members respectively of thewing frames or trusses, the intermediate members of which are indicatedat do in Fig. 10 and need not be further described. The wings are thusconnected to and supported from the frame 55, the wing trusses beingrigid and being connected to the frame at four spaced points and thusbeing rigid therewith.

The hollow shafts or tubes I09 extend in parallel relation, and tubularbushings IIO are disposed between bearings 86 and tubes I08 thussurrounding said tubes, members I I0 being made of resilient materialsuch as rubber. The members I09 are also embraced by bearings or lugsIII which are also split or capped and are secured to the sides of amotor I l 2. The motor I I2 is thus supported by and suspended from theframe 55 and hangs quite a distance below the frame as shown in Fig. 10.It will also be seen that there is resilient connection between theframe and the motor. Motor H2 is, of course, of the internal combustiontype and while different types of motors might be used, in theembodiment of the invention illustrated, a motor having verticalcylinders and a horizontal crank shaft is illustrated.

An auxiliary frame designated generally I I6 is provided, and this frameis rigidly connected to the tubular members or shafts I09 carried bysaid main frame and this frame is thus connected to motor II2. Frame IIBcomprises four upwardly extending and converging corner pieces I I! andH9 and H9 and I20, which members are welded at their lower ends tomembers I09. The forward members H1 and H8 which are also in the form oftubes, extend upwardly and rearwardly in converging relation and areconnected by a series of horizontal members I2I welded thereto at theirends. Members III and H8 are also connected by the diagonal members I23which, like members I2 I, are in the form of tubes and are welded tomembers In and II8 substantially at the junction therewith of membersI2I. Members H9 and I20 at the rear of the frame are also connected bythe horizontal cross members I23 which are also in the form of tubes andwelded to said members at their ends. It will be seen that the membersH9 and I20 converge from members I 09 to the second cross member I23 andthen extend upward in parallel relation. Members H9 and I20 are alsoconnected by the diagonal members or tubes I24 which are welded theretoat their ends closely adjacent the ends of horizontal members I23. Thepair of members I I! and I I9 and the pair of members I I8 and I20 arerespectively connected by the horizontal members I25 and the diagonalmembers I26 also in the form of tubes and welded to said pairs ofmembers at their ends. Members H1, H8, II 9 and I20 as stated are weldedto members I09 and gusset plates I21 are provided, set into and weldedinto said members and members I09. Gusset plates I28 are also set intomembers H9 and I20 and welded thereto and to members I09 as well as tothe lower horizontal member I23. Gusset plates I29 are also set into andwelded to members Ill and H8 as well as to the members I09 and also areset into and welded to the lower cross member I2I. The frame IIG has atits top the U-shaped plate I 30 shown in Figs. 4 and 12 to 14. Tubes H1,H8, H9, I20, I24 and I28 are welded at their upper ends to plate I30. Abracket I3I is bolted to plate I30 at me top or auxiliary Irame llli,which bracket has bearings therein in which is journaled a shaft I32 towhich the hub 45a of a propeller 45 is secured. Shaft I32 carries abeveled gear I34 meshing with the beveled gear I35 in turn secured to avertical shaft I36. Shaft I36 is journaled in a bracket I33 secured tothe rear of motor H2 and has secured to its lower end a beveled gearI38. Beveled gear I38 meshes with a beveled gear I39 secured to thecrank shaft of the motor I I2. Propeller 45 is thus driven through gearsI38 and I39, shaft I36 and gears I34 and I35. Frame II6 thus forms apartial support for this drive transmission and for the propeller 41.Frame II6, of course, also forms the frame work for the tower 44.

The hull 40 comprises longitudinally extending frame members I40 and MM,members I40a being at the lower corners of the hull as shown in Fig. 20and members I40 being at the bottom some distance from the members I40a.Similar members HI and I4Ia extend longitudinally of the hull at theupper portion thereof, member I4I being at the upper outer corner andmember I4 Ia being disposed some distance. inwardly of member I4I. Acentral keel member or keelson I42 extends longitudinally of the hull atthe bottom central part thereof and keelsons I43 extend longitudinallyof the hull also at the bottom at equal distances at each side of thekeel I42. The members I40 to I43 are preferably made from laminatedWood. The keel I42 comprises a lower wood portion MM and a verticalrib-like portion upstanding therefrom at the center thereof. The hull 40is provided with an offset or step 40b some distance in front of therear portion of the tower 44 and the structure of the keel at this stepportion is shown in Figs. 24 to 27. In Fig. 24 the laminations are shownand it will be seen that the top group of laminations I42b arecontinuous. The lower portion I42a of the keel is cut off as shown atM20 and a wedge I44 of the width of the upper portion of the keel isdriven forwardly into the keel between the lower portion MM and theupper narrow portion. The lower group of laminations MM is widened outas shown in Fig. 27 to form the lower portion of the keel from the stop40b rearwardly. The laminations I42?) and MM are thus continuous and arenot interrupted by the step 40b. The hull also comprises spacedlongitudinally extending members or battens I45 also of laminatedstructure and transversely extending members I46 of laminated structurewhich are cut out to receive the longitudinally extending members I45.The hull has extending transversely thereof at intervals, bulkheads, oneof which is shown in Fig. 20. The section in Fig. 20 is taken through aportion of the hull containing the wheel pocket and the bulkheadtherefore does not extend entirely to the outer side of the hull. Thebulkhead comprises the outer vertical members I41 and the inner membersor bow I48, the latter being of U-shape and extending around the centralpart of the hull forming a recess in which is disposed the motor II 2.Forward of the motor, bow I48 is omitted and the space between membersI41 at each side will form the cockpit. a floor (not shown) being builtsome distance above the keel I42. At the rear of the motor I I2 bow I48is also omitted and top member I49 and plate or board II extend fromside to side of the hull. Member I41 and bow I48 are, as shown in Figs.21 and 22, rectangular in cross section and are connected by thetransverse members I49 and I50. A thin plate or board I5I is secured toone side of the members I41 and I48 and extends throughout the fulllength of said members as well as member I46 at the bottom of the hull.Said plate I5I is strengthened by having secured thereto the V-shapedribs I52. At the lower part of the hull another plate I53 is secured tothe other side of members I41, I40 and' member I46. Blocks I54 aredisposed between the plates I5I and I53 and are recessed to receive thekeelson members I43. Another block I55 is set in between the plates I5Iand I53 at the central portion thereof and is recessed to receive thecentral keel member I42. Spaced stiffening members or battens I 56extend longitudinally of the hull at the outer side of the bulkhead,member I41 being recessed to receive the same. A thin board or sheet I41is used for the bottom of the hull and a covering I58 of similarmaterial is used for the side of the hull, this covering being securedto the transverse and iongitudinally extending members I45 and I46 atthe bottom and I41 and I56 at the sides, as well as to members I40, I40aand I4Ia. The compartment within the sheets I51 and I58 is, of course,absolutely water-tight. The lower sheet I51 extends outward as stated,to member I 4011 and another sheet I59 is provided, which extends upwardfrom member I40a, being secured to the outer side of member M011 andmember I4I. Sheet I59 is also secured to the longitudinally extendingmembers I60 and the vertically extending members I 6| which arerectangular in cross section, members I 6| being recessed to receive themembers I60. Transverse partitions I62 extend from the sheet I59 to aninner sheet I63 which is disposed in a vertical plane. Vertical membersI6Ia extend along the outer side of sheet I 63 while longitudinallyextending members I 6Ib extend along the outer side of sheet I63, beingrecessed into members I6Ia. Sheet I63 is secured to members I6Ia andI6Ib. Members I6Ia are secured at their bottoms to member I40a. A topsheet or thin board is disposed over the top of the hull between membersI48 and MI, the same being shown as having an opening I64a therein abovewheel pocket I 61 to accommodate the landing wheels when retracted. Thecompartment between members I58 and I63 designated I61, forms the wheelcompartment into which the wheels are retracted when the plane is on thewater, and said compartment is closed at its ends by suitable bulkheadsand partitions as indicated by the dotted lines I65 and IE6 in Fig. 1. Adeflector or deflecting plate I 61a is disposed at the rear side of thewheel pocket or compartment I61 and extends across the same. This plateas shown in Figs. 5 and 34 curves upwardly and forwardly from the lowerpart and rear portion of said pocket or compartment. The bottom of thecompartment which forms part of the sheet or covering I51 is in the formof a door I68 hinged by the hinge I69, so as to open downwardly asindicated by dotted lines in Fig. 20. The compartment is arranged to bedrained by a siphon tube I which, as shown in Figs. 20 and 23, is ofinverted U-shape and secured to the inner side of compartment I61 by aclip I1l secured to wall I58. The rear end of the tube I10 is open asindicated at I10a a short distance above the door I68 and the front endis provided with a flange I10b secured to the bottom I51 in the rear ofdoor I68. Said flange surrounds a hole I51a through floor I51 and aspout member I12 has a flange I12a engaging the outer side of sheet I51.This flange and flange I101) are bolted together 'lrll through floor I51by headed and nutted bolts I 13.

The hull 48 is supported by the frame 55 at four points, namely at thejunction of tubes 62 and 53, the junction of tubes 6| and and thejunction of tubes 53 and I88 at the ends of member or tube 53. The jointor connection between the frame and hull is shown in Figs. 17 to 19,this being the joint at the junction of tubes 6| and 5| and adjacent thejunction of tubes I82 and I83. An angle plate I15 is provided, and thishas an upper portion extending through a slit in the tube 6|, said plateand tube being welded together. Said plate extends to and around thetube 5| and has a flange I15a at right angles to the axis of tube 6|which extends lengthwise of the tube 5| and is welded thereto. A bracketI16 also in the form of an angle plate is provided. and this has flangesat right angles to each other, one of which engages plate I15 and isconnected thereto by the headed and nutted bolt I11 and the other flange|16a of which engages flange H511 and is bolted thereto by the headedand nutted bolt I18. The bracket I16 extends vertically along thevertical member I19 at the inner side of the hull, being bolted throughthe same and the sheet or covering of the hull I58 by the headed andnutted bolt I88. Said bracket is also bolted through the longitudinallyextending member him of the hull and the outer sheet by the headed andnutted bolt IBI. Flange I16a of the plate I16 is bolted by the headedand nutted bolt I82 through a pair of spaced cross pieces I83 whichextend across the top of the hull. Plate I16 also has a lug |16b bentinto a plane parallel with the flange I16a but extending in the oppositedirection and along the side of a vertical member I19 of the hullsimilar to the member M1. Another vertical member I85 is shown, spacedslightly from member I19. Another plate I86 is provided, and this platehas a wide flange I86a extending along the inner side of member I Ma.and secured thereto by headed and nutted bolts I81. Flange I86a is alsobolted to the hull by head-ed and nutted bolts I88 which also extendthrough a filler block I84. Bolts I81, I88, and bolts I88 and I8I alsoextend through a flange I861) which is disposed flat against the outerside of the hull and against the sheet or covering I58. The plate I86has formed thereon a semi-cylindrical portion I860 at the sides of whichare flanges IBM, and plate I86 is also bent downwardly at right anglesto flange I86d to form flange I861). Flanges I86a and I86b are thusparallel and as stated, are connected by bolts I88, I8I, I81 and I88.Plate I86 also has a flange I86e extending at right angles to flangeI86a which is also bolted to flange I15a by the headed and nutted bcltI18. Flange I86b is also bolted to flange "6:1 by the bolt I82. A fillerpiece I9I is disposed between flanges I86e and I16a. Flange I86a alsohas a lug I86f bent parallel to flange I862 but extending oppositelythereto and alongside of vertical member I85, being bolted thereto bythe headed and nutted bolt I92 which also extends through member I19 andthe lug "61). A cap member I93 is provided, having a central cylindricalportion and spaced parallel ribs I93a disposed in vertical planes, saidcap also having a flange I83b bolted to the flange I86d by the headedand nutted bolts I94.

From the above description it will be seen that the hull is supportedfrom the main truss frame I 55 by plate I15 and through plates I16 andI86.

The hull is secured to the rear portion of the frame as shown in Figs. 8and 8a by bracket 208.

It may be stated that the lugs II3 formed at the ends of the main framefor the attachment of the wing frames are formed of the tubes 30.surrounded by and welded to plates II 3b which are set into and weldedto the ends of tubes 58, 5|, 52 and 53, as shown in Fig. 8a. An angleplate 28I has flanges 28Ia and 28Ib at right angles to each other,flange 28 lb extending through a slit in and being welded to the tube 53and flange 28Ia also being welded to tube 53. A bracket 288 has flanges288a and 28Gb at right angles to each other, and these are boltedrespectively to flanges 28 Ia and 28 lb by the headed and nutted bolts282. Flange 2881) is also bolted to a rib 283 extending transverselyacross the top of the hull by the bolt 284 and flange 288a is boltedthrough a vertical member 285 of the hull by the headed and nutted bolts286, these bolts also passing through a plate 281 disposed flat againstthe outer side of the covering of the hull. Plate 288 also has a lug2880 extending at right angles to flange 288a and parallel and in theopposite direction to the flange 28% which engages the side of thevertical member 285 and is bolted thereto by bolt 288. Another bracket289 is dis posed at the side of flange 28Ib opposite bracket 288 and hasa flange 289a shaped similarly to flange 28% and bolt 284 also passesthrough this flange and another cross rib 2I8 parallel and ad jacent thecross rib 283. Bolt 282 also passes through flange 289a. Bracket 289 hasa flange 289D which, like the flange 208a, is bolted by bolts 2 to avertical rib 2I2 adjacent rib 285. Bolts 2 also pass through plate 281which is wide enough to aline with both flanges 288a and 28%. It will benoted that the upper bolts 286 and 2H also pass through a longitudinallyextending member I4I at the upper outer corner of the hull. It will thusbe seen that the hull is connected to the rear portion of the framethrough plate 28| and the plates or brackets 288 and 288. The hull isthus suspended from the main truss frame 55 at four points.

The bearing formed by flange I860 and the cap I93 has journaled thereina tube 2I4 which extends transversely of the hull as shown a shortdistance in front of and below the front lower tube 5| of the trussframe 55. It will be under stood that there is one of the bearingshaving the cap I93 at each side of the hull. Shaft 2M is also journaledin a capped bearing 2I5 welded to plates 2|6 and Zn which are connectedto the hull by the bolts 2I8 which extend through a vertical member 2I9and a filler block 2|9a as shown in Fig. 29. A landing gear is providedfor the plane and this comprises a pair of members 228 in the form oftubes which are bolted at their upper ends to sockets 2I4a which arewelded in turn at their upper ends to tube 2M. Members 228 have collars22I secured thereto, and at their lower ends telescope respectively intotubes 222. The latter tubes have collars 223 secured thereto and betweencollars HI and 223 a multiplicity of resilient washers 224 made ofrubber or similar material are disposed. Members 222 have secured attheir lower ends the bearings 225 in which are journaled the axles ofthe landing wheels 226 which as usual will be equipped with pneumatictires 221. Members 222 are shown as bifurcated at their lower ends andbolted to the caps 225a of the bearings 225 which have central ribswelded thereto embraced by the members 222 and connected thereto byheaded and nutted bolts 2251). The tubes or members 222 are dividedintermediate their ends and the portions thereof connected by the hinge226, said members having ends 222a adapted to contact when member 222 isin a straight line position. A guide member 229 in the form of anarcuate plate is secured to the inner wall I56 of the wheel compartmentI61 by a plurality of spaced screws 230. Said member 229 has its endscurved and at its lower end is reversely bent into U-shape to form aslot 23I and axle bearing 225 has a cylindrical projection receivable inslot 23I and which moves in engagement with the concave edge of plate229. Said bearing also has secured thereto a rod 232 which is pivoted atits other end on a stud 233 carried in a bearing 234 having a circularflange secured to the inner wall I58 by the screws 235. Member 2 I4 hasan arm 236 secured thereto and this arm is pivotally connected at itsouter end to a link 231 which is pivotally connected to a screw 239.Screw 239 is threaded into a nut 242 carried in a bearing 24I secured tothe longitudinal member I4 Ia. Nut 242 has thrust collars 242a at itsends engaging the ends of bearing 24I. Nut 242 is secured in and weldedto a tube 240 which extends forwardly to a bracket 249 secured to theforward end of the hull which has bearings for the tube 246. A beveledgear 245 is secured to tube 240 and meshes with another beveled gear246. Beveled gear 246 is secured to a shaft journaled in bracket 249which has at its inner side a crank handle 248 by which it can beturned.

With the described construction, it will be seen that when crank 248which is in position to be conveniently manipulated by the pilot isturned, member 240 and nut 242 will be turned and the thread therein issuch that members 240 and 91-11 will be drawn together or moved apart.This oscillates arm 236 and oscillates the hollow shaft or tube 2I4.When shaft 2I4 is oscillated, members 226, 222 and 224 will be swungfrom the full line position shown in Fig. 28 to the dotted line positionshown therein. Bearings 225 will be lifted and the inner bearing will beguided along the concave side of the guide member 229 and will swingabout the axis of stud 233 and engage the upper curved end of the guidemember 229. In this operation it will be seen that member 222 breaks andswings about the hinge 228 and the wheel 226 is thus moved to the dottedline position and is disposed within compartment I61 and with its bottomabove the bottom of said compartment. It will be seen that when thewheels are swung down and are in contact with the ground, that theWeight of the plane is transmitted through the main frame 55 and tube 2I4 to the members 220 and through the resilient members 224 which act asshock absorbers to the wheels 226. The aeroplane is thus supported bythe wheels 226 and by the trailer wheel 46.

As stated, the bottom of the wheel compartment is closed by a door I68.A mechanism is provid for opening and closing this door as the wheel isprojected or retracted. This mechanism includes an arm 250 securedrigidly to tube 2I4 so as to oscillate therewith. Arm 256 has securedthereto one end of a cord or cable 25I which extends downward over apulley 252 and has its end secured at 253 to a curved arm 254 swingabieabout the pivot 255 carried in a bracket 256 having a flange which isbolted to the inner wall of compartment I61 adjacent the bottom thereof.Arm 254 has a pin 251 at its end rigidly carried therein, and said pinis movable in a slot 258a of a bracket 258 which is secured to the innerside of door I66.

When tube 2 I 4 is oscillated to project the wheels 226, arm 236 isswung to pull upon the cable 25'. This swings arm 254 about its pivot2'35 and pin 251 moving in slot 258a swings door I68 about its hinge I69to the open position shown in Figs. 29 and 30.

The outer member 222 just above axle 225 has secured thereto a pulley259. A cord or cable 260 runs over this pulley and under a pair ofpulleys 26I disposed at either side respectively of the pulley 259 andcarried in small brackets 262 secured to the inner side of the door I68.From pulleys 26I the cord 260 extends over another pulley 263 carried ona bracket 264 secured to the inner side of door I68 and said cord hassecured to its end a pin 265 travelling in the elongated slot 266a ofbracket 266 secured to the inner side of the door I68 parallel to itsend portions. There is a bracket 266 at each end of door I68 and a pin265 at each end of cord 260, one only being shown.

With the described construction, when member 222 is elevated and movesupward, pulley 259 moves along guide member 229 close to the innerbearing 225. This pulls upward upon cable 260 and the same passing overits various pulleys, pulls upon pins 265. These pins thus exert aclosing movement upon door I68. The doors, of course, tend to drop bygravity, and after a short movement from the fully open position shownin Fig. 30, the closing tendency increases and the doors are quicklyswung to closed position as pulley 259 moves to its upper position. Thedoor I69 is thus opened and closed and at all times under the control ofthe cables 25I and 260 as the wheels are projected or retracted.

Should the plane be used without the doors I 68, the water would passsomewhat into the compartments as shown in Fig. 34, wherein the water isdesignated 280. This water will, as the plane is in motion, take acourse as indicated and will be deflected out of the compartments by thedefleeting plates I61a. Even without the doors, therefore, thecompartments will be kept almost free of water when the plane is inmotion on the water.

The usual controls for the rudders and ailerons will be located in thecockpit in the customary positions convenient for manipulation by theoperator.

The motor H2 is air-cooled and for this purpose a casing indicated bythe dot and dash line 216 is provided, (see Figs. 4 and 5) enclosing themotor II2. This casing has an opening 21I in the top of the wingdirectly in front of the tower 44 shown in Figs. 4 and 5. An opening 212may also be formed in the front and lower side of one wing at one sideof the portion over the hull and this opening is connected by passage213 with the top and front end of the casing 210. An exhaust passage 214is provided for casing 210 and this opens in the rear of the tower 44.It will be understood that there is an area of high pressure when theplane is moving, at the points of the openings HI and 212 and there isan area of low pressure in the rear of the tower at the exhaust opening214. Air will thus move through casing 210 at high velocity to cool themotor. It may be stated that the exhaust pipes of the motor extendthrough an outer chamber indicated in Fig. 6 as 215. Air will also passthrough this casing to keep the exhaust pipes cool, so that there willbe no danger of the same setting fire to the plane.

When the plane alights on the water, the water will enter thecompartment I61 substantially to the depth of the draft of the plane,such water being indicated as 216 in Fig. 23. As the plane moves forwardon the water after doors I68 are closed, the water will be siphoned outthrough the pipe I ID as there will be an area of low pressure in therear of spout I12 and the water will draw through the pipe I10 asindicated by the arrows in Fig. 23.

In Figs. 35, 36 and 3'7 a modified form of structure is shown forsupporting the hull. In these figures the tubes I02 and I03 are shownconnected to tube 5| and tube 6| instead of having the supporting plateI65 welded thereto is enclosed in a cap bearing having the cap 28I andthe bearing portion 282. Bearing 282 and cap 28I have mating flangesconnected by headed and nutted bolts 283. Bearing portion 282 has adepending plate 282a analogous to the plate I15 shown in Figs. 17 to 19,and this plate has bolted thereto the plate I16, said plates beingconnected by bolt I11. Bearing 282 and its cap 28I embrace a bushing 284of resilient material such as rubber, which bushing surrounds tube 6| sothat the parts supported by bearing 282 are resiliently supported fromtube 6|. In place of the plate II5a being welded to tube 5|, said tubeis embraced by a bearing 285 and its cap 286, said bearing and caphaving mating flanges connected by the headed and nutted bolts 281. Aplate 285a is integral with the bearing 285 and extends downwardly andlaterally therefrom, the same being connected by bolts 288 to flangeI'I6a of bracket I16. Bearing 285 and its cap 286 embrace a resilientbushing 289 of rubber or similar material so that the parts supported byplate 285a are resiliently supported from tube 5|. The parts of the hulland brackets connected to the same, as well as the bracket I86 and itscap I93 are the same as shown in Figs. 17 to 19.

In the structure shown in Figs. 35 to 37, the hull is resilientlysupported from the frame at its forward end, and similar cap bearings,not shown, with resilient bushings, may be used for supporting the hullfrom the rear end of the frame. With such a construction, bracket 20Iwould have its plate 20Ia secured to a bearing embracing tube 63 andhaving a cap thereon, and would have its plate 28Ib secured to a bearingembracing tube 53 and having a cap thereon. Resilient bushings would, ofcourse, embrace tubes 53 and 63 and be embraced by said bearmgs.

By using the resilient bushings embracing the tubes of the frame, thehull is resiliently supported and any vibration of the frame would belargely absorbed in the resilient bushings so that it would not betransmitted to the hull.

It will be understood that the term hull is used herein to mean eitherthe fuselage of a land plane or the body of a flying boat or seaplane.

From the above description it is seen that applicant has provided anovel and very efficient structure of aeroplane. The structure has ahigh degree of strength with a very small weight and at the same time arugged and rigid support is furnished for the hull while the motor andattached parts are securely but resiliently supported.

The landing gear is effectively supported from the main frame in asimple and efiicient manner. As stated. the plane is constructed andarranged to alight either on land or on the water. When landing on wateras above described, the operator will retract the wheels andsimultaneously close the doors to the wheel compartments. The wheels arethus not projecting in any way to give a retarding effect, as the hullmoves through the water. The hull is shaped to operate efliciently as aboat.

By suspending the motor from the main frame and suspending the hull fromthe main frame, the center of gravity is brought quite low, the samebeing located just below the top of the hull proper and forward of thewing center. This gives great stability to the plane. This is of greatimportance when the plane is in the water, as it practically eliminatesthe tendency of the plane toward lateral instability. It is unnecessary,therefore, to have wing floats at the wing tips. When flying, the lowcenter of gravity gives a pendulum effect, affording great stability.The compact concentrated loads make the plane easy to maneuver. Whenlanding, the location of the center of gravity relative to the wheelsand the disposition of the hull relative to the wheels prevent the planefrom nosing over.

The location of the propeller is such that there is practically nointerference with the propeller action and the flow of air through thepropeller is smooth and unobstructed, giving an increased efficiency. Itwill be noted that by locating the propeller rearwardly of the pilot andpassengers, there is no slip-stream from the propeller to strike thepassengers in the face and with the present location of the propeller,there is no slip stream blast over the fuselage. The absence of the slipstream blast over the fuselage, which occurs when the propeller is atthe nose of the plane, greatly reduces the air resistance on the hull.The propeller being in the rear of the pilot and passengers, there is noobstruction in front of the pilot seat and perfect visibility can be hadforward, sideward and downward. The absence of projecting parts alsoenables the plane to have an attractive and ornamental appearance. Thisalso greatly reduces air resistance. It may be mentioned that the spacewithin the sides of the frame 55 will be used to carry oil and gas aswell as baggage and the batteries. Any radio equipment can also becarried by this frame.

The plane can also be maneuvered readily. The concentrated weightincluding the motor, oil and gas, as well as the pilot and thepassengers, are massed in a comparatively small space or volume. Thismakes it easier to swing the plane in flight.

It will also be noted that there are no appreciable stresses on thehull. The wing stresses and stresses due to the concentrated loads aretaken by the central frame 55. The resilient mounting of the motorprevents the vibration from the motor and power plant being transmittedpositively to the frame and the rest of the aeroplane.

The fact that the center of gravity of the plane is quite low, makes itpossible to have the wheels much closer together. With the low center ofgravity and the wheels close together, there is a very small tippingmoment. Having the wheels close together also makes it possible toretract the wheels into the hull.

It will, of course, be understood that various changes may be made inthe form, details, arrangement and proportions of the parts. withoutdeparting from the scope of applicant's invention, which generallystated, consists in a device capable of carrying out the objects aboveset forth, in the parts and combinations of parts disclosed and definedin the appended claims.

What is claimed is:-

1. An aeroplane structure having in combination, a central frame havinggroups of members in three planes, the longitudinal central axis ofmembers of said groups converging at approximately one point, a hullhaving groups of frame members, disposed in three planes intersecting atone point, and means connecting said frame and bull substantially atsaid points respectively.

2. An aeroplane structure having in combination, a central trunkportion, a main frame of truss formation disposed in said trunk portionincluding a group of three truss members, the central axis of whichconverge substantially to a common point, a hull and means connectingsaid hull to said frame closely adjacent said point, said hull havingframe members intersecting adjacent said means and being suspended fromsaid frame.

3. An aeroplane structure having in combination, a central trunkportion, a main frame of truss formation disposed in said trunk portionincluding a group of three truss members, the central axis of whichconverge substantially to a common point, a hull, means connecting saidhull to said frame closely adjacent said point, said truss framecomprising four of said groups having said three members in each, saidhull being connected to said frame adjacent each of said four groups,two of said groups being at one side of said hull and two at the otherside of said hull.

4. An aeroplane structure having in combination, a central wing section,a main central frame of truss construction and of substantiallyrectangular form within said section, separate side wing sectionsextending at each side of said frame having wing frames therein securedto said main frame, a hull independent of said main frame except that itis suspended therefrom, a motor suspended from said main frame independently of said hull and disposed principally within said hull, apropeller supported above said central wing section and means fordriving said propeller from said motor.

5. An aeroplane structure having in combination, a central wing section,a main central frame of truss construction and of substantiallyrectangular form in outline disposed within said wing section, separateside wing sections at each side of said central wing section having wingframes therein secured to said main frame, a hull disposed below saidcentral wing section and main frame and independent of said main frameexcept that it is suspended therefrom, a motor suspended from said mainframe independently of said hull and disposed principally within saidhull, an auxiliary frame of truss formation secured to said main frame,a propeller mounted on said auxiliary frame and means for driving saidpropeller from said motor.

6. The structure set forth in claim 5, said auxiliary frame extendingupwardly above said central wing section, a tower extending from the topof said central wing section and enclosing said auxiliary frame, thesame being stream-lined longitudinally of said aeroplane and saidpropeller being at the rear and upper end of said tower.

'7. An aeroplane structure having in combination, a central wingsection, a main central frame of truss construction and of generalrectangular shape within said section, separate side wing sectionsextending at either side of said central frame having wingframes thereinsecured to said main frame, a hull independent of said main frame exceptthat it is suspended therefrom, said main frame having amotor-supporting portion adjacent its bottom, a motor suspended at aplurality of points from said portion and disposed principally belowsaid frame and principally in said hull, a propeller mounted above saidmain frame and means for driving said propeller from said motor.

8. An aeroplane structure having in combination, a central wing section,a main central frame of truss construction and of general rectangularshape disposed within said wing section, separate side wing sectionsdisposed at either side of said central section having wing framestherein secured to said main frame, a hull independent of said mainframe except that it is suspended therefrom, said main frame includingforwardly and rearwardly extending spaced members, a motor detachablysecured to and suspended from said members and disposed principallybelow said main frame, an auxiliary frame of truss constructionsupported rigidly on said members and extending upwardly therefrom abovesaid central wing section, a propeller carried by said auxiliary frameand means for driving said propeller from said motor.

9. An aeroplane structure having, in combination, a central wingsection, a main central frame of truss construction and of generalrectangular shape within said section, separate side wing sections ateither side of said central section having wing frames therein securedto said main frame, a hull independent of said main frame except that itis suspended therefrom, said hull being resiliently carried by andinsulated from said main frame and disposed below said frame and centralwing section, a motor independent of said hull resiliently suspendedfrom and insulated from said main frame and disposed principally withinsaid hull, a propeller above said central Wing section and means fordriving said propeller from said motor whereby stresses from said hulland motor are transmitted to said main frame, a shock absorbing means isprovided between said hull and frame and between said motor and frameand there is no electrical path between said motor and frame.

10. An aeroplane structure having in combination, a central wingsection, a main central frame of truss construction and of substantiallyrectangular form within said section, separate side wing sectionsextending at each side of said frame having wing frames therein securedto said main frame, a hull independent of said main frame except that itis suspended therefrom and below the same, said main frame including twopairs of longitudinally spaced bearings, spaced forwardly and rearwardlyextending motor-supporting members received in said pairs of bearingsrespectively and a motor suspended from said members having bearingsenclosing said members, said motor being disposed principally in saidhull, said first mentioned hearings including removable cap portions,said supporting members being removable upwardly when said cap portionsare removed.

11. The structure set forth in claim 10 and a unitary rigid auxiliaryframe of truss formation rigidly connected to said motor-supportingmembers and extending above said central wing section, a propellermounted at the top of said auxiliary frame and means for driving saidpropeller from said motor.

RUFUS R. RAND, JR.

